Tow target apparatus for high speed flight



Sept. 20, 1960 R J, HQPPER ETAL 2,953,442

TOW TARGET APPARATUS FOR HIGH SPEED FLIGHT Filed OC'. 22, 1955 3 Sheets-Sheet 1 Sept. 20, 1960 R, 1 HOPPER ET AL 2,953,442

` TOW TARGET APPARATUS FOR HIGH SPEED FLIGHT 5 Sheets-Sheet 2 Filed Oct. 22. 1956 Spt. 20, 1960 R. .1. HoPPER ETAL 2,953,442

Tow TARGET APPARATUS RoR HIGH SPEED FLIGHT Filed oct. 22, 195e 3 Sheets-Sheet 3 am r n. f e

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m f if United Patented Sept. 20, 1960 TOW TARGET APPARATUS FOR HIGH SPEED FLIGHT Robert J. Hopper, deceased, late of Pacific Palisades,

Calif., by June Wesley Hopper, executrix, Pacilic Palisades, and Boyd B. Elder, Los Angeles, Calif assgnors to Del Mar Engineering Laboratories, Los Angeles, Calif., a corporation of California Filed Oct. 22, 1956, Ser. No. 617,569I

21 Claims. (Cl. 273-1053) This invention relates to apparatus for aerial target practice, and, more particularly, relates to the combina- Ition of a tow target `and a launcher for use on an aircraft to transport the tow target in stowed position to a practice area and to launch the tow target on a tow cable for a target run.

One problem to which the invention is ldirected is to provide such a vcombination that may be used advantageously with a ktowing aircraft that flies at high speeds in or near the supersonic range. Heretofore, the launcher and the stowed tow target carried thereby for transportation to and from a practice 'areav have provided a composite configuration having too much drag for use on an exceptionally high speed aircraft; even the launcher Ialone as heretofore constructed has had too much drag and too much flutter vibration for an exceptionally high speed aircraft; and the usual tow target ying at the end of a long tow cable has been characterized by drag that is excessive for exceptionally high speed target runs. The invention meets this problem by providing a low drag composite configuration for the combined launcher and stowed target, by providing a low drag configuration for the launcher `alone and. by providing a low drag configuration for the tow target alone.

A feature of the invention is that a number `of different purposes, all working together to make high speed target runs feasible, are accomplished by providing the tow target with a slender, tapered, elongated probeflike nose member that is rigidly united with the tow target and with the cooperation of the launcher is capable of supporting the tow target body.

With reference to the configuration of the tow target alone, the addition ofthe slender, tapered elongated nose probe is an addition to the area of the tow target that, considered alone, increases the skin friction, but this drag-increasing factor is more than offset by other drag-reducing factors. One yof the offsetting factors is that the lengthening of the tow target by the `addition of the nose probe increases the distance of the tow cable connection from the center of gravity of the tow target, and thus increases the inherent stability of the tow target to such an extent that the size of the stabilizing tail fins of the tow target may lbe substantially reduced.

The reduction in skin friction by reduction of the size of the tail fins is much greater than the skin friction added by the nose probe. Another offsetting factor is that moving thertow cable connection forward to la greater distance from the center of gravity `decreases the departure angle of the tow cable relative to the axis of the tow target and thus reduces the drag of the tow cable. For these reasons, the addition of the nose probe reduces the over-all drag to make the tow target suitable for exceptionally high speed flight. t A Y With reference to the conguration of the launcher alone, the fact that the slender nose probe is capable of Ysupporting the tow target,:bodyY makesit possible to dimension the launcher to engage only the nose probe of the tow' target. Thus, the launcher may be of the general character of a cylinder of relatively small diameter having a suitable streamlined nose. The slender launcher may be mounted on a slender streamlined pylon to provide a low drag arrangement that is highly satisfaCtQl'y for aircraft designed for supersonic iiight.

With reference tothe composite configuration of the launcher and the tow target when the tow target is in stored position, the launcher telescopes over the nose probe of the tow target and merges with the configuration of the tow target body. Since the launcher is substantially smaller in cross section than the tow target body, it forms, in effect, a nose for the tow target. For lthese reasons, the composite coniiguration has relatively low Idrag in the range of high speed flight.

Further aspects of the invention relate to the solution of certain problems that arise in the use of a launcher of the character described with a towV ta-rget of the character described. One of these problems is that the optimum angle of the launcher relative to the aircraft for normal cruising flight is different from the optimum angle for `either launching or retrieving a tow target. During launching and retrieving the launcher should be in approximate alignment with the inclined position the tow `target takes when it is airborne. Such alignment minimizes stressing the tow target in flexure during a launching operation and facilitates guiding the tow target nose probe into the launcher during a retrieving operation. In this regard, an important feature of the preferred practice lof the invention is the mounting of the launcher on the tow aircraft to `tilt by remote control from a normal position to a target-retrieving position, the target-retrieving position being inclined in accord with the angle of attack of the tow target.

Another problem is that the tow target rotates on its longitudinal axis for stability in flight and excessive stress in torque in the nose probe structure may be incurred by snubbing the nose probe in the launcher. A feature of one practice of the invention in this regard is, in elfect, to make at least the trailing portion of the launcher of rotary `construction to permit free rotation of the snubbed target. Another solution is the provision of a noncircular portion of the launcher for engagement with a noncircular portion of the tow target in the region of the base of the nose probe to immobilize the tow target against rotation without stressing the nose probe itself.

Still another problem arises -in those instances in which the tow target has forward turbine blades to derive power from the =air stream for various purposes. The problem is to avoid damage to these blades by impact with the launcher, especially during the operation of retrieving a tow target when the tow target tends to over run the launcher. Fortuitously the provision of the nose probe solves this problem by making it possible to space the turbine yblades -a substantial distance rear- Ward from the connection with the tow cable.

As will be explained, other features of the invention relate to the problem of automatically and releasably latching the tow target in its stored position and the problem of providing expelling force for launching the .tow target at Ithe beginning of a `target run.

The Various features and advantages of the invention will be apparent in the following detailed description considered with the accompanying drawings.

ln .the drawings, which are to be regarded `as merely illustrative:

Figure l is a side elevation of a high speed jet aircraft equipped with a selected .embodiment of `the invention with the reel for the tow cable at a location on the aircraft outside the launcher;

Figure 2 is an enlarged longitudinal sectional View of the launcher and the leading end of the .tow target with the tow target engaged and supported by the launcher;

Figure 3 is a transverse section taken as indicated by the line 3 3, showing how yan elongated launching means inside the launcher is guided by a forward set of rollers;

Figure 4 is a similar cross section taken `along the line 4 4 of Figure 2, showing a second rearward set of guide rollers;

Figure 5 is a view partly in side elevation and partly in section, showing the construction of the elongated launching means;

Figure 6 is a transverse section of the launching means taken as indicated by the langular line 6 6 of Figure 5;

Figure 7 is a side elevational view similar to Figure l, showing how the launcher may be tilted relative to the ai-rcraft for launching or retrieving the tow target;

Figure 8 is a fragmentary view partly in side elevation and partly 4in section, showing the remotely controlled mechanism for tilting the launcher;

Figure 9 is ya fragmentary perspective view illustrating a second practice of the invention in which the launcher holds the stored tow target against rotation;

Figure l -is a fragmentary sectional view taken as indicated by the line id lii of Figure 9, showing how the leading end of the ltow target engages the trailing end of the launcher;

Figure ll is a side elevational `of `a high speed air craft embodying `a form of the invention in which the reel for the tow cable is incorporated in the launcher itself and is capable of retrieving the tow target; and

Figure l2 is` an enlarged portion of Figure ll with parts broken away.

Figure l, illustrating a selected practice of the invention, shows a tow target, generally designated by the letter T, in snubbed position on a high speed jet aircraft 20 -for transportation to and from a target practice area. As best shown in Figure 7, the tow target T has a slender, tapered, elongated nose probe 22 to which the tow cable 24 is connected and this nose probe is of sufficient strength and rigidity to support the streamlined body of the tow target. A slender, elongated launcher, -generally designated by the letter L, having a tapered streamlined nose 25, is iixedly mounted on the under side of the aircraft wing 26 by a slender streamlined pylon 28. In the stowed position of the tow target T, the nose probe 22 is .telescoped into and engaged by the launcher L for cantilver support of the tow target, as shown in Figure l.

t is to be noted that the launcher L is only as large in cross section as needed for telescopic engagement with the nose probe 22. Thus, the concept of employing a slender, elongated nose probe rfor suppont of the tow target in stored position makes it possible to use a relatively slender launcher suitable =for high speed flight, and also makes it possible for the stored tow target to combine with the launcher to provide `a composite streamlined configuration for thigh speed iiight.

The tow target T has a set of tail fins 30 which are preferably of slightly angular configuration to cause the tow target to rotate on its longitudinal axis for increased stability -in flight. The configuration of the tow target T, separate and `apart from the launcher L, is su-itable for high speed flight, the provision of the nose probe 22 being of primary importance in accounting for the exceptional aerodynamic efficiency of the configuration, :as heretofore explained.

In the -initial embodiments `of the invention, the diameter of the base portion of the nose probe .22 is of the order of magnitude of l to 20% of the maximum diameter of the tow target. For example, a tow target used successfully at flight speeds somewhat under the supersonic range has a body of 18 inches maximum diameter and a nose Vprobe 3 inches in diameter at its base. For flights `at supersonic speeds the tow, target may have a maximum body diameter of 15 inches and `a nose probe of 3 inches diameter at its base. It has been found to be satisfactory to use a nose probe as long las one and one-half times the maximum body diameter of the tow target.

As indicated in Figure 2, the body of the tow target T may be in .the form of a shell having a thin wall 32. Such a shell may be made in sections, each section being of molded paper construction of relatively light weight.

The nose probe 22 may be the exposed forward portion of a thin-walled tubular aluminum member 34 that extends into the interior of the tow target body and is supported therein .in la manner for distributing the towing stresses to the thin wall 32 of the body. For this purpose, the concealed base portion of the tubular member 34 may be connected to ring-shaped members or bulkheads that are bonded to the thin wall 32. Thus, Figure 2 shows `a tapered internal reinforcement ring 35 that embraces the tubular member 34 `and is bonded to the inner surface of the thin body wall 32. For increased rigidity, the tubular aluminum member 34 has a core 36 of suitable material, which, -in this instance, is a foamed cellular plastic.

Since the tow target T spins on its longitudinal axis for stability, the cable 24 is connected to the nose probe 22 by means of a rotary joint. In the construction illustrated by Figure 2, the tapered forward end of the tubular member 34 fixedly embraces a fitting 38 having a threaded extension 40 of reduced diameter. A tapered sleeve 42 is screwed onto the threaded extension 40 and secured thereon by a pair of dowels or crosspins 44, the purpose of the tapered sleeve being to mount a pair of ball bearings 45. A .clevis member 46 for attachment to the cable 24 has an axial stem 48 journaled in the ball bearings 45. Preferably, the tow cable 24 is provided at its end with an eye fitting 50 that is connected to the clevis member 46 by a crosspin 52.

The launcher L has a cylindrical body shell 54 which is formed with the previously mentioned streamlined nose 25. Rotatably mounted on the trailing end of this body shell is a rotary ring member 55 which is internally tapered, as shown, to nest or seat the forward end of the tow target in the region of the base portion of the nose probe 22. In the construction shown, the rotary ring seat 55 is journaled in a ball bearing 56 inside a bearing ring 58 that telescopes into the body shell 54 and is secured thereto by fastening elements 60.

Mounted inside the launcher shell 54 is an elongated means 62 which may be termed a launcher or carriage member. This launcher or carriage member has a rearwardly directed socket 64 to serve as seating means for the clevis member 46 at the tip of the nose probe 22, and is formed with a rearwardly directed bell mouth 65 to guide the clevis member into the socket. The launcher or carriage member 62 is guided longitudinally with minimum friction by suitable rollers that track in longitudinal guide grooves 66 (Figure 3) in the launcher member. In the construction shown, there are four guide grooves that are engaged by a forward set of four rollers 68 in forward brackets 70 and are also engaged by a rearward set of four rollers 72 in rearward brackets 74.

The launcher member 62 is shown in its forward retracted position in Figure 2 and is movable to a rearward extended position at which the bell mouth 65 is at the rear open end of the launcher, as indicated in dotted lines at 75. The launcher member 62 is continuously urged towards its rearward extended position by suitable yielding means which may take the form of four longitudinal coil springs '76. These springs may be connected at their rearward ends to the rearward brackets 74 and connected at their forward ends to a radial flange 78 on the forward end of the launcher member.

In this embodiment of the invention, the tow cable 24 is wound. ontoA a suitable reel 80t outside of thek launcher L, the reel being mounted .inside the narrowpylcn 28'. As best shown in. Figure 8, the cable. 24 engages two guidel pulleys 81 and 82 carried by the pylon 282 and passes' under a third guide pulley 83 inside the launcher L, the tow cable extending rearward fromthe third guide pulley throughy the tubular launcher member 62 to. its connection with the clevis member y46. The tow cable 24 also passes through a normally open cable cutter, generally indicated 84, which. isy of well known type that contains an' explosive charge to generate cutting force. The explosive charge may be detonated electrically by remote control'. i

It is apparent that the tow cable` 24 maybe placed under tension to hold the tow target T in engagement with the launcher L in the manner shown in Figure 2, with the clevis member 46 in the socket 64 and with the launcher member 62 in its forward fully retracted position. A feature of this particular embodiment of the invention, however, is the provision of suitable latch means t'o retain the clevis member 46 in the socket 64 and the further provision of suitable latch means to retain the launcher member 62 in its forward retracted position.

The rst latch means for engaging. the clevis 46 may be in the form of a latch member 85 positioned in a longitudinal slot 86 of the launcher memben'; and mounted on a suitable pivot pinv 88. The latch member 85 is formedi with a nosei 90"y to.z engage the rear shoulder 92 of the clevis member, as shown in Figure 2, and the latch member is further formed with a forwardly extending nger 94 that engages the inner surface of the launcher member to keep the latch member from swinging downward from the' position shown. Thus, with the latch member 85 maintained inthis position, the entrance of the clevis. member y46.4 into the; socket 64 causes the rounded leading end of the clevis.` member to lift the latchv member with aI camming action, the nose of the latch falling. behind the. clevisA shoulder 92 when the clevis member is fully seated: in the socket 64; This entrance of the clevis member into the socket. 64 occurs when the launcher member 62 is. at its rearward extended position where the latch member 85 is free to swing upward. When the launcher member 62. is in its forward fully retracted' position, however, the. latch member 85 is positioned' under the uppermost guide roller 72, as shown in: Figure 22.,.andv is thereby immobilized. to lock the clevis. member in, the socket 64.

The second latch means for releasably holding the launcher member 62 in its fully retracted forwardI position may comprise a pawl 95l in the form of the armature of a remotely controlled solenoid 96. The pawl 95 is urged to the eifective positiontshown. in'. Figure 2; by a concealed spring and is formed with. an inclined end face 98. When the launcher member 62 is retracted forward by the cable 24 after the clevis member 46 seats in the socket 64, the radial ange 78 of the launcher member, moving against the inclined end. facel 981,. retracts the pawl 95 and the pawlk subsequently. drops into its effective position. behindA the radial flange.,

While the launcher L may be ixedly mounted on the pylon 2S, an important feature. of this particular ern.- bodiment of the invention. is that the launcher may be tilted by remote control from the normal ight position shown inFigure l, in. which the longitudinal axis of the launcher is substantially paralleli tothe fore andi aft axis. of. the aircraft, to` the inclined position shown. in

dotted lines in Figure 7, the purpose ofv the inclinedA position being to facilitate the retrieving of. the tow target T after a' target practice run. The means for mounting and controlling the launcher L with respect: to tilt may be constructed as indicated in Figure 8.

The launcher L has a. forwardrupper' hinge fitting 1100 that is concentric to. the guide. pulley 82' and!v isconnected rby a. hinge pin 10210i a secondV hinge tting 104 onr the; forward wall. of the' pylon suitable bell'- crank 105 is mounted byV a pivot pin 106 on a bracket 108 on the under side of the pylon 28 and one arm of the -bellcrank is connected to one end of a link 110 by a pivot pin 112. The second end' of the link 1'10 isconnected by a pivot pin 114 to a bracket 115 on the upper side of the launcher. The secondi arm of the bellcrank 1-"05 is pilvotally connected to aVtraveling nut 1'16 on a power-actuated screw 11S'. The screw 111'8- extends from a cylindrical gearcase 120 containing suitable reduction gearing driven by a remotely controlled' motor 122`. The cylindrical.' gearcase- 120i is swingly mountedr by a pivot pin 124 on a bracket 125 on the inner wall of the pylon 28. v p

Normally, the launcher L is held in its upper position against the undersurface of the pylon 28 by the described mechanism in the manner shown in Figure 8, with the traveling nut 1116 at its retracted forward position to cause the short linkv `110i to be heldf in an upper position inside the pylon. Actuation of the screw 118 by remote control of the motor 102 shifts the traveling nut 116 tov a position on the screw to extendf the described linkage for tilting the launcher downwardy as indicated by the*V dotted lines in Figure 8.

In the preferred practice of they invention, a pair oflimit switches. 126 and 1128 are adjustably mounted on a support bar 130 that is parallel with the screw 118I and is supported by a suitable bracket 132 on the cylindrical gearcase 120. Thus, when the motor 122 is ener-- gized in either direction, it' is autom-atically cut off at a limit position by the movement of the traveling nut 1.16 against one of the two limit switches. With thet air speedV of the aircraft 20'V known in advance, the angle. of attack of the tow target T may be ascertained for' that air speed and the rearward limit switch 128 may be'` adjusted on the support bar 130 to de-energize the motor 122 when the launcher L reaches the angle of inclination corresponding to the angle of attack of the tow target.v

The manner in which the described apparatus oper-- ates for its purpose may be readily understood from the' foregoing description. In preparation for a target flight, the tow target T is pulled intothe launcher L by winding rotation' of the reel 80 to latch the clevis member 46 in the socket 64 and to latch the launcher member 62 at its forward retracted position. With the tow target T engaging the launcher L inthis manner, the combined or composite coniguration formedV by the launcher and tow target is an air-streamed configuration having sufficiently low drag: to make it possible for the airplane toiiy at relatively highV speed'- to the practice areay where a target run is to be commenced.

When the practice area is reached, it is desirable to tilt the launcher as heretofore explained. Then the solenoid 96 is energized lby remote control from al control station on the aircraft- 20 to retract the pawl 95, and the reel `permits the tow cable 24 to slacken sufficiently to permit the launchingv of the towtarget, The four coil springs 76` thrust the launching member 62 rearward to itslimit position with the radial flange 78 against the roller brackets 70 to. carry the tow target rearwardly and to thrust the same fully into. the air. stream. As the launcher member 62 moves initially out of its normally forward retractedposition, the latch member moves out from under the associated guide roller 72 and is thereby freed-for release movement. When the launcher member 62 reaches its fully extended rearward position, the nose of the latch member 85 is cammed by the clevisl member 46 out of'v engagement with the clevis member shoulder 92 to avoid interference with the launching operation: Once the tow target is completely disengagedfrom the launcher L, it assumes its normal angle of attack and the reel 80 may play out the tow cable 24 toposition the tow target at the desired distance from the towing aircraftY 20.. The tow target T is caused to spin about its longitudinal axisby the slight angularity of the tail fins 30 and the rotary swivel 46 permits this rotation of the tow target independently of the tow cable 24.

If, for any reason, it is desirable to jettison the tow target T at any time when the tow target is being towed, the cable cutter 83 may be energized by remote control to sever the tow cable 24. In some instances the reel 80 is a one-way reel which functions during flight only to unreel the cable 24 in a controlled manner, and in such instances, the cable cutter is used as a matter of routine. In other instances, the reel 86 is a two-way reel capable of winding in the cable during flight to retrieve the tow target.

In a retrieving operation, as the reeling in of the tow cable 24 brings the tow target T near the aircraft 20, the motor 122 is energized by remote control to tilt the launcher L downward, as shown in dotted lines in Figure 7, the inclination of the launcher approximating the angle of attack of the tow target. With the launcher L inclined in this manner, the nose probe 22 is at least approximately axially aligned with the launcher L and readily enters the launcher without being subjected to any substantial bending stress.

Initially, the clevis member 46 makes contact with the rearwardly extending bell mouth 75 of the launcher member 72 and is guided thereby into the socket 64, the spring-loaded launcher member 72 acting as a shock absorber to decelerate the tow target. As the clevis member 46 reaches its completely seated position in the socket, the nose of the latch member 85 drops behind the shoulder 92 of the clevis member. The continued reeling of lthe tow cable 24 causes forward retraction of the launcher member 62 in opposition to the springs 76 to carry the target inwardly of the launcher shell until the radial flange 78 of the launcher member is automatically engaged by the pawl 98. As the launcher member 62 reaches its fully retracted forward position for complete seating of the tow target, the latch member 85 is immobilized by the associated guide roller 72, as heretofore explained.

The tow target T rotates about its longitudinal axis as it approaches the launcher L and it continues to rotate after it is fully engaged by the launcher. Normally, the clevis member 46 is sationary in the socket 64 when the parts are positioned as Vshown in Figure 2, the rotary mounting of the clevis member permitting the tow target to continue to rotate. The rotary seat 55 snugly engages the forward end of the tow target in the region of the base of the nose probe 22, and thus engages and supports the nose probe region of the tow target at a second point without interfering with the freedom of the tow target to rotate about its longitudinal axis. It i-s apparent that this provision of a rotary swivel member 46 in combination with a rotary seat 55 at the trailing end of the launcher eliminates the possibility of the tow target being subjected to excessive stress in torque by its supporting engagement with the launcher.

If desired, the rota-ry seat 55 at the trailing end of the launcher L may be omitted. Thus, as indicated in Figures 9 and 1G, the Itrailing end o-f a launcher L may be provided with a fixed circular Seat 134 for supporting engagement with the tow target in the region of the base of the nose probe 22. The tow target is -imrno- -bilized by the launcher Iagainst rotation by engagement of a noncircular portion of the tow target with a noncircular portion of the fixed seat 134. For this purpose, the target T' may be :formed with a radial lug 135 and the fixed circular seat -134 may be formed with a radial recess 136-to receive the radial lug. As the rotating tow target T is drawn into the launcher L by reeling in the tow cable 24, the tow target continues to rotate until it makes frictional contact with the circular seat i134 and until the lradial lug `135 is drawn into the radial recessV 136. `In all other'respects, this modified 8 form of the invention is constructed and operated in the manner heretofore described.

Figures 11 and 12 show an embodiment of the invention comprising the combination of a two-way launcher 137 and a tow target 138. The two-way launcher 137 is self-contained in that it not only includes a reel 138 but also contains power means in the form of an air turbine 140 for actuating the reel. The reel 139 and the air turbine 140 are of the same general construction 'and arrangement set forth in the Hopper et al. Patent 2,751,167, issued lune 19, 1956 and entitled, Reeling Apparatus for Controlling aTow Cable From an Aircraft, which disclosure is hereby incorporated in the present disclosure by reference.

The housing of the launcher 137 is mounted on the wing 142 of an aircraft 144 by the usual pylon 145 and comprises an enlarged forward housing portion 146 and a trailing housing portion 148 of smaller diameter. The forward housing portion 146 includes the reel 139 and its mechanism. 'Ihe trailing portion 148 is of the same general construction as the previously described launcher L.

As shown in Figure 12, the [reel 139 may be in the form of a spool that is slidingly mounted on a square shaft 150 for rotation therewith. The reel is reciprocated on the square shaft by a level wind mechanism which includes at least one shaft '152 with a continuous helical thread 154 thereon. The tow cable 155 passes from the reel 139 around an adjacent `guide pulley 156 and then passes around three rearward guide pulleys 158, 159 and 160 to lenter the trailing housing portion 148 axially thereof.

T-he tow target 138 to which the tow cable 155 is attached, is of the same `general character as the previously described tow target T, but is equipped with an air turbine 162 for energizing certain devices in the tow target that are utilized in target practice but need not be described. The tow target 138 is of the usual configuration with the usual nose probe 22 by means of which it may be releasably supported by the trailing housing portion 148.

Since the two-way launcher is employed to retrieve the tow target 138 after a target run by winding in the tow cable 155, it is highly improbable that in the retrieving operation the tow target will over run the rear housing portion of the launcher. A highly irnpor-tant advantage o-f the new tow target configuration, however, is that the air turbine 162 is located near the base end of the nose probe 22. As the target is retrieved, the tow cab-le will be coaxially Vdrawn into the launcher to insure that the leading end lof the probe is first introduced into the launcher and before any other portion of the target is brought into close proximity with the launcher. In this manner, the air turbine is spaced suciently rearward from the point of connection of the tow `cab-le y to the leading end of the probe to keep the air turbine from making damaging contact with the launcher when the tow target over runs, the launcher. The possibility of damage to the air turbine 162 is further reduced by mounting the launcher 137 on the pylon 145 to tilt into general alignment with the return path of movement of the tow target during the retrieving operation, the tilting mechanism being concealed in Figure 12.

Our desciiption in specific `detail of the selected embodiments of the invention will suggest various changes, substitutions and other departures from our disclosure within the spirit and scope of the appended claims.

What is claimed is:

1. In an aerial target apparatus, the combination of: a tow target having a tapered nose portion; a tow target launcher for mounting on an aircraft for supporting the target for transportation in stored position on said launcher to the area of a target run, said launcher having a rotary trailing portion to seat said nose por- 'spaanse tion at the stored position of the ktarget and to permit the stored tow target to rotate; a tow cable for extension from the interior of the launcher to tow said target on a target run; `and connecting means rotatably mounted on the leading end of said nose portion for attaching said tow cable to the nose por-tion and to permit rotation of the stored tow target in said rotary trailing portion of the launcher relative to the cable.

2. A combination as set forth in claim l in which fthe internal structure `of said launcher includes latch means to engage said rotary connecting means to hold the tow target iny stored position.

3; In an aerial target apparatus, the combination of: a tow target having a nose portion; a tow target launcher for mounting on an aircraft for transportation of the tow target in stored position to the area of the practice run; a tow cable for extension from the launcher to said nose portion to tow said target on a target run; means included in the internal structure of said launcher to seat said nose portion, said seating means being movable relative to the fixed structure of the launcher from a rearward extended position to receive said nose portion to a forward retracted position for holding said target body in stored position; and latching means on said seating means for positive engagement with said tow target in response to the forward retraction of the seating means.'

4. A combination as set forth in claim 3 in which said latching means includes a latch member movably mounted on said seating means; and which includes means xedly mounted on the launcher to lock said latch means at the forward retracted position of the seating means, and to release the latch means when the latch means is extended rearward.

5. In an aerial target apparatus, the combination of: a tow target; a tow target launcher for mounting on an aircraft for transportation of the tow target in stored position to the area of a target run; and rotary means connecting said tow cable to the leading end of said tow target, said launcher -having a rotary portion to seat the forward end portion of said tow target to permit rotation of the tow target about its longitudinal axis when the tow target is supported by said launcher.

6. A device for releasably supporting an aerial tow target on an aircraft fitted with a tow cable and reel for reelin-g the tow target in and out relative to the aircraft, comprising: a hollow body for mounting on the aircraft longitudinally thereof, said hollow body being open at its trailing end to form a seat for a portion of said tow target that is spaced rearwardly from the leading end of the tow target; carriage means mounted inside said hollow body for movement longitudinally thereof between a rearwardly extended position with the rear end of the carriage means at said trailing end of the hollow body and a forwardly retracted position, the rear endA of said carriage means being hollow to receive the leading end of said tow target; yielding means urging said carriage means towards its rearward extended position; means to automatically latch the leading end of the tow target to said carriage means in response to retraction of the carriage means by said tow cable pulling the leading end of the tow target `against the carriage means; and remotely releasable latch means to hold said elongated means in its retracted position.

7. A combination as set forth in claim 6 in which said automatic Vlatching means comprises: a latch member on said carriage means to engage said leading end; and means at a fixed position inside said hollow body to immobilize said latch means in response to the retraction movement of the elongated means.

v8. A device for releasably storing an aerial target on an aircraft and for launching the target from the aircraft during flight, comprising: a hollow body for mounting on the aircraft longitudinally thereof, said body being open at its trailing end to form afi-rst seat for engaging a portion of said target that is spaced rearward from the lead end of the' target; elongated means mounted inside said hollow body for movement longitudinally thereof between a rearward extended position with .the rear end of the elongated means at said trailing end of the hollow body, and a forward retracted position, the rear end of said elongated means forming a second seat to receive the leading end of the target; means to thrust said elongated means rearward from its forward retracted position thereby to thrust said target from its stored position into the air stream; a first latch means to hold the leading end of the target in said second seat for storing the target, and a second latch means to hold said elongated means at its forward retracted position for storing the target.

9. A combination as set forth in claim 8 in which said thrusting means is a spring means normally restrained by said second latch means.

l0. An aircraft aerial tow target system, comprising: an elongate rigid tow target including a body member having `a forwardly tapered streamlined configuration; an elongate nose probe coaxially projecting forwardly beyond said forwardly tapered configuration, said nose probe being rigid for cantilever support of said body member; a reel apparatus to be carried by the aircraft for controlling a tow cable secured to the free end of said probe; an open-ended hollow support member substantially longer than said nose probe to be secured to the aircraft with the open end facing rearwardly thereof for telescopically receiving said probe; a rearwardly facing seat carried by said support member at the open end thereof within the cross-sectional dimensions of the support member and adaptedto supportingly nest at least the forward portion of the target; cable guide means mounted for movement within said support member relative to said seat coaxially thereof and passing said cable longitudinally of said support member, said cable guide being dimensioned to telescope over the leadingend of said nose probe for positive engagement therewith; and resilient means normally urging said cable guide means to a position adjacent the open end of said support member, whereby said guide means is adapted to engage with the probe of said target and to retractingly move coaxially of saidV supportr member to center and to absorb the impact of said tow target relative to said support member as the nose probe of the target is drawn into said support member and the forward portion of said target engages saidsefat as the cable is wound on` said reel apparatus to draw said target to said support member.

11. A device for releasably holding an aerial tow target having :an elongate probe coaxially projecting forwardly of the nose thereof to an aircraft fittedv with a reel apparatus carrying a tow cable to which the probe ofk said target is aflixed and operable to play out said cable, comprising: a support member including ian elongated, hollow body openl at one end thereof; means for mounting said hollow body to the aircraft with the open end thereof facing rearwardly of the aircraftV whereby saidl probe may be telescopically received therein; said hollow body providing at the open end thereof a ring element within the cross sectional dimensions of the body to form anV annular seat for nestingly engaging a portion of the target spaced rearwardly from the leading end of the probe of said target; carriage means coaxially mounted within said hollow body for movement longitudinally thereof between a rearwardly extended position in which the rear end of the carriage means is adjacent and coaxially disposed relative to said seat and a forwardly retracted position, said carriage means being hollow for passing said cable and for telescopically receiving the leading end of the probe of said tow target forV positive engagement therewith; means carried by the rearward end of the. carriage means for engaging the leading end of said probe; and resilient means urging said carriage means towards its` rearwardly extended position,Y

whereby a resilient thrust is-applied to said nose probelto 11 eject the target from said support member when the reel apparatus is operated to play out said cable.

12. A device for releasably holding an `aerial tow target having a substantially long probe coaxially projecting forwardly of the nose thereof to an aircraft fitting with a reel apparatus carrying a tow cable to which said target is affixed and selectively operable to play out and retrieve said cable, comprising: a support member including an elongated hollow body open at one end thereof; means for mounting said hollow body to the yaircraft with the lopen end thereof facing rearwardly of the aircraft; a ring element at the open end of the body within the cross-sectional dimensions of the body and forming an annular seat for nestingly engaging a portion of the target spaced rearwardly from the leading end of the probe of said target; elongate tubular means coaxially mounted within said hollow body for passing said cable longitudinally of said support member; support and guide means associated with said tubular means for mounting said tubular means within said support member for movement longitudinally thereof between a rearwardly extended position in which the rear end of the elongated means is adjacent and coaxially disposed relative to said seat and a forwardly retracted position with the range of longitudinal movement substantially entirely within the interior Iof said support member; means carried by the rearward end of said tubular means for telescopically receiving the leading end of said probe having positive engagement therewith; resilient means urging said elongated means towards its rearwardly extended position, said last named means yielding as said probe is telescopically passed into said support member to eng-age the target with said seat and operable to apply a thrust to said tubular means as the cable is played out from said reel apparatus, thereby ejecting said target from said support member for tow by said cable.

13. A device for releasably holding an aerial tow target having an elongate probe coaxially projecting forwardly of the nose thereof to an aircraft fitted with a reel apparatus carrying a tow cable to which said target is affixed and operable to play out said cable, comprising: a support member comprising an elongated hollow body member open at one end thereof; means for mounting said body member to the aircraft with the open end thereof facing rearwardly of the aircraft; a ring element coaxially carried by the open end of the body member within the cross-sectional dimensions of the body member and forming an annular seat for nestingly engaging a preselected portion of the target spaced rearwardly from the leading end of the probe of said target; a tubular element dimensioned to telescopically receive the leading end of said nose probe for positive engagement therewith; support and guide means, including a plurality of roller members, for coaxially mounting said element within said hollow body member for passing said cable longitudinally of said support member; said support and guide means mounting said tubular element for movement longitudinally of said body member between a rearwardly extended position in which the rear end of the elongated means is adjacent and coaxially disposed relative to said seat and a forwardly retracted positi-on with the range of longitudinal movement substantially entirely within the interior of said support member; resilient means normally urging said tubular element towards its rearwardly extended position yand yielding as said probe is engaged with the rear end of said tubular element and telescopically nested within said body member for engagement of the preselected portion of the target by said seat; said resilient means applying an `ejecting force to said tubular element as said cable is played out from said. reel apparatus, whereby the tubular element forces said probe outwardly of said body member to eject the target from said support member.

14. In an aircraft tow target installation including a reel apparatus for controlling a cable to which the target is secured, a combination of: a streamlined tow target body having low drag aerodynamic characteristics for high speed flight having a relatively long nose probe projecting coaxially forward of the target body, said nose probe being rigid for cantilever support of the tow target body and being connected to said cable; a support member to be secured rigidly to the aircraft with said cable extending through the support member, said support member being smaller in cross-sectional dimension than said target body `and having a rearwardly facing open end -of a larger cross-sectional dimension than said nose probe for telescopically admitting said nose probe into said support member to rigidly support said target body for transit to the area of the target practice area; said support member being of an elongated streamlined configuration for relatively low drag during flight and being of substantially a smaller cross-sectional dimension than the tow target to merge rigidly with the tow target body configuration to form therewith a composite streamlined configuration of relatively low aerodynamic drag when said nose probe is telescopically nested within said support member and the target body is supported by said support member.

15. A device for releasably holding an aerial tow target having an elongate probe coaxially projecting forwardly of the nose thereof to an aircraft tted with a reel apparatus carrying a tow cable affixed to the leading end of said probe and selectively operable to play out and retrieve said cable, comprising: a launcher including an elongate streamlined, hollow body member open at one end thereof; means for mounting said launcher to the aircraft with the open end of said launcher facing rearwardly of said aircraft, said mounting means including means for moving said launcher between a normal support position for transporting the tow target in the flight of the aircraft and a downwardly angled second position for retrieving the tow target as the cable is wound upon said reel apparatus after a towed iiight of the target, said downwardly inclined second position approximating the course of the target as it is drawn into the launcher thereby facilitating entry of said nose probe into said launcher; a seat element carried at the open end of said launcher for receiving and supporting at least the forward portion of said tow target contiguous to said nose probe; and means carried within said launcher, including a cable guide element movable relatively to said seat element coaxially thereof for passing the cable longitudinally of said body member and for holding the cable out of engagement with said launcher, said guide element centering the course of the cable as it is drawn into said launcher and thereby centering said nose probe of the target as it is drawn into said launcher under the urging of the cable as the latter is reeled in by said reel apparatus to telescopically fit the nose probe within said launcher and to supportingly nest the forward portion of said tow target against said seat element.

16. A combination as set forth in claim l5 in which said moving means includes means for varying the angle of inclination of said launcher in the said second position whereby said launcher may be caused to assume a predetermined angle of inclination in accord with an anticipated angle of attack of the tow target as it is drawn toward said launcher under the urging of the cable as the same is wound upon the reel apparatus.

17. A device for releasably holding an aerial tow target having an elongate probe coaxially projecting forwardly ofthe nose thereof to an aircraft fitted with a reel apparatus carrying a tow cable to which said target is affixed and operable to play out said cable, comprising: a hollow body member open at one end thereof; means for mounting said body member to the aircraft with the open end thereof facing rearwardly of the aircraft for telescopically receiving the forwardly projecting probe of the tow target; an annular seat element carried by the body member at ,the open end thereof for nestingly supporting the forward portion of said target; and resilient ejector means mounted within said body member for movement substantially coaxially of said body member and adapted to engage with the nose probe of said target for resiliently urging said nose probe outwardly of said body member when said cable is played out from said reel apparatus, said mounting means including means for moving said body member from a position in which the longitudinal axis of the body member is substantially parallel with the fore and aft axis of the aircraft to an alternate position in which the body member is downwardly and rearwardly inclined relative to the fore and aft axis of the aircraft.

18. A device for releasably holding an aerial tow target carrying spin-producing fin elements and having an elongate probe coaxially projecting forwardly of the nose thereof to an aircraft fitted with a reel apparatus carrying a tow cable to which said target is affixed and selectively operable to play out and retrieve said cable, comprising: a launcher including an elongate hollow body member open at one end thereof; means for mounting said launcher means to the aircraft with the open end of said launcher facing rearwardly of said aircraft; a seat element at the open end of said launcher within the cross-sectional dimensions of the launcher for receiving and supporting at least the forward portion of said tow target contiguous to said nose probe; and means carried within said launcher, including a cable guide element movable relatively to said seat element coaxially thereof for holding the cable out of engagement with said launcher, said guide element centering the course of said cable as it is drawn into said launcher and thereby centering the course of said nose probe as it is drawn into said body member of the launcher under the urging of the cable as the latter is reeled in by said reel apparatus to telescopically lit the nose probe within said launcher and to supportingly nest the forward portion of said tow target against said seat element, said seat element being rotatably carried by said body member and rotatable with said target as the latter is rotated by the action of the airstream on the fin elements thereof in the flight of the aircraft.

19. An aerial tow target installation, comprising: an aerial tow target having an elongate rigid probe coaxially projecting forwardly of the nose thereof of strength for cantilever support of the tow target; a launcher open at the rear end thereof for mounting on the aircraft in the air stream thereof, said launcher being substantially longer than said nose probe and the open end of said launcher being of a larger cross-sectional dimension than the nose probe of said target whereby said nose probe may be telescopically received into the launcher for support of said target thereon for transport to the area of a tow target practice run, said launcher being of a streamlined, elongate configuration having low drag aerodynamic characteristics and being of substantially smaller cross-sectional dimension than the tow target to merge with the tow target conguration to form therewith a composite streamlined configuration of relatively low drag when said nose probe is telescopically received within the launcher for cantilever support of the tow target; a reel apparatus for mounting to the aircraft; and a tow cable carried by said reel apparatus and passed longitudinally of said launcher, the reel apparatus being selectively operable to play out and retrieve said cable; said tow cable being connected to the leading end of said nose probe whereby said nose probe may be telescopically drawn into the open end of said launcher as the cable is wound upon said reel apparatus and released therefrom as said cable is unwound from said reel apparatus.

20. A device for releasably holding `an aerial tow target carrying tins for aerodynamically rotating said target and having an elongated probe coaxially projecting forwardly of the nose thereof to an aircraft tted with a reel apparatus carrying a tow cable to which the probe of said target is aixed and operable to play out said cable, comprising: a support member including an elongate hollow body open at one end thereof; means for mounting said hollow body to the aircraft with the open end thereof facing rearwardly of the aircraft, whereby said probe may be telescopically received therein; said hollow body providing at the open end thereof a ring element within the cross sectional dimensions of the body to form an annular seat for nestingly engaging a portion of the target spaced rearwardly from the leading end of the probe thereof and including means co-acting with the said portion of the target, as the latter moves into a preselected position relative to said seat, for holding said target against rotation; carriage means mounted within said hollow body for movement longitudinally thereof between a rearwardly located position in which the rear end of the carriage means is adjacent and coaxially disposed relative to said seat and a forwardly retracted position, said carriage means being hollow for passing said cable and for telescopically receiving the leading end of the probe of said tow target; means carried by the rearward end of the carriage means for engaging the leading end of said probe; and resilient means urging said carriage means toward its rearwardly located position whereby a resilient thrust is applied to said nose probe to eject the target from said support member when the reel apparatus is operated to play out said cable.

21. A device for releasably holding an aerial tow target having an elongated probe coaxially projecting forwardly of the nose thereof to an aircraft fitted with a reel apparatus carrying a tow cable to which the probe of said target is affixed and operable to play out said cable, comprising: a support member including an elongate hollow body open at one end thereof; means for mounting said hollow body to the aircraft with the open end thereof facing rearwardly of the aircraft whereby said probe may be telescopically received therein, said mounting means operable to tilt said support member relative to said aircraft from a normal position for normal flight to a second position in which the rearwardly facing end of the hollow body is below the forwardly facing end as the cable is wound upon the reel apparatus for facilitating retrieving of the tow target; said hollow body providing at the open end thereof a ring element within the cross sectional dimensions of the body to form an annular seat for nestingly engaging a portion of the target spaced rearwardly from the leading end of the probe thereof; carriage means movably mounted within said hollow body for movement longitudinally thereof between a rearwardly located position in which the rear end of the carriage means is adjacent and coaxially disposed relative to said seat and a forwardly retracted position, said carriage means being hollow for passing said cable and for telescopically receiving the leading end of the probe of said tow target for positive engagement therewith; means carried by the rearward end of the carriage means for engaging the leading end of said probe; resilient means urging said carriage means toward its rearwardly located position whereby `a resilient thrust is applied to said nose probe to eject the target from said support member when the reel apparatus is operated to play out said cable.

References Cited in the file of this patent UNITED STATES PATENTS 2,122,766 Wiemer July 5, 19'38 2,137,450 Green Nov. 22, 1938 2,243,618 Brown May 27, 1941 2,272,213 Lear Feb. 10, 1942 2,432,371 Berberich Dec. 9, 1947 2,502,650 Harris Apr. 4, 1950 2,667,351 McKinney Ian. 26, 1954 2,751,167 Hopper lune 19, 1956 2,778,584 Wilson Ian. 22, 1957 2,805,065 Cotton Sept. 3, 1957 2,813,719 Hopper Nov. '19 ,1957

FOREIGN PATENTS 737,318 Great Britain Sept. 21, 1955 UNITED STATES PATENT oEEICE CERTIFICATION OF CORRECTION Patent No. 2,953,442 September 20, 1960 v Robert J. Hopper et al.

It is hereby certified that error appears in the above numbered patent requiring correction and that the said Letters Patent should read as corrected below.

Column 9, lines 62 and 69, for "elongated" read carriage Signed and sealed this 25th day of April 1961.

(SEAL) Attest:

ERNEST w. SWTDER DAVID L, LADD Commissioner of Patents Attesting Officer 

6. A DEVICE FOR RELEASABLY SUPPORTING AN AERIAL TOW TARGET ON AN AIRCRAFT FITTED WITH A TOW CABLE AND REEL FOR REELING THE TOW TARGET IN AND OUT RELATIVE TO THE AIRCRAFT COMPRISING: A HOLLOW BODY FOR MOUNTING ON THE AIRCRAFT LONGITUDINALLY THEREOF, SAID HOLLOW BODY BEING OPEN AT ITS TRAILING END TO FORM A SEAT FOR A PORTION OF SAID TOW TARGET THAT IS SPACED REARWARDLY FROM THE LEADING END OF THE TOW TARGET, CARRIAGE MEANS MOUNTED INSIDE SAID HOLLOW BODY FOR MOVEMENT LONGITUDINALLY THEREOF BETWEEN A REARWARDLY EXTENDED POSITION WITH THE REAR END OF THE CARRIAGE MEANS AT SAID TRAILING END OF THE HOLLOW BODY AND A FORWARDLY RETRACTED POSITION, THE REAR END OF SAID CARRIAGE MEANS BEING HOLLOW TO RECEIVE THE LEADING END OF SAIT TOW TARGET, YIELDING MEANS URGING SAID CAR- 